Propeller blade static detection device and blade static detection method

Abstract

The application provides a propeller blade static detection device and a propeller blade static detection method, and relates to the technical field of equipment measurement. The propeller blade static detection device comprises a base, a clamping mechanism arranged on the base, a pressure detection mechanism and an optical detection mechanism. The pressure detection mechanism and the clamping mechanism are arranged on the preset side of the base. The optical detection mechanism is slidably arranged on the bottom of the base to slide on the plane perpendicular to the bottom. The clamping mechanism is used for clamping and fixing the measured blade. The pressure detection mechanism is used for collecting the pressure data of the measured blade to detect the physical attribute parameters of the measured blade. The optical detection mechanism is used for collecting the optical data of the measured blade to detect the size data of the measured blade. The application reduces the time for measuring the blade and improves the accuracy of measuring the blade.

Description

Technical Field

[0001] This application relates to the field of equipment measurement technology, and more specifically, to a method for static detection of propeller blades. Background Technology

[0002] As a key component of rotorcraft, the performance of the rotor blades directly affects the flight quality and safety of the aircraft. There are many static inspection items for rotor blades, including blade weight, center of mass, static balance, airfoil tolerance, blade tip height, blade pitch angle, and blade length. The inspection of these parameters is crucial to ensuring the static balance and aerodynamic shape of the rotor blades.

[0003] Currently, different tools are typically used to measure rotor blades of rotary aircraft. Therefore, different measuring tools need to be clamped separately before measuring the blades.

[0004] However, repeatedly clamping the measuring tool is difficult and time-consuming, which increases the measurement time for the blade. Furthermore, the repeated clamping of the measuring tool affects its measurement accuracy, resulting in a large error in the measurement of the blade. Summary of the Invention The purpose of this application is to address the shortcomings of the prior art by providing a propeller blade static testing device and a propeller blade static testing method, so as to reduce the time for propeller blade measurement while improving the accuracy of propeller blade measurement.

[0005] To achieve the above objectives, the technical solutions adopted in the embodiments of this application are as follows: In a first aspect, one embodiment of this application provides a propeller blade static testing device, the propeller blade static testing device comprising: a base, a clamping mechanism disposed on the base, a pressure testing mechanism, and an optical testing mechanism; The pressure detection mechanism and the clamping mechanism are disposed on a predetermined side of the base; the optical detection mechanism is slidably disposed on the bottom of the base so as to slide on a plane perpendicular to the bottom. The clamping mechanism is used to clamp and fix the blade under test. The pressure detection mechanism is used to collect the pressure data of the blade under test to detect the physical property parameters of the blade under test. The optical detection mechanism is used to collect the optical data of the blade under test to detect the external dimensions of the blade under test.

[0006] Optionally, the physical property parameters include: weight; the pressure detection mechanism includes: a first pressure sensor, which is disposed on the preset side; The first pressure sensor is used to collect the gravity data of the blade under test, so as to calculate the weight of the blade under test based on the gravity data.

[0007] Optionally, the physical property parameters further include: the position of the center of mass and the static moment; The pressure detection mechanism further includes a second pressure sensor, which is disposed on the preset side. The second pressure sensor is used to collect auxiliary pressure data of the blade under test, so as to calculate the center of mass position and static torque of the blade under test based on the auxiliary pressure data and the weight.

[0008] Optionally, the first pressure sensor is a three-point support pressure sensor, and the second pressure sensor is a knife-edge balanced pressure sensor.

[0009] Optionally, the physical property parameters further include: the position of the center of mass and the static moment; The pressure detection mechanism further includes: a first torque sensor, a second torque sensor, and a third torque sensor, all of which are fixedly mounted on the preset side. The first torque sensor, the second torque sensor, and the third torque sensor are respectively used to collect the first torque data, the second torque data, and the third torque data of the blade under test, so as to calculate the center of mass position and static torque of the blade under test based on the first torque data, the second torque data, and the third torque data.

[0010] Optionally, the dimensional data includes: length, blade tip height, airfoil tolerance, and blade pitch angle; The optical inspection mechanism includes: a two-dimensional optical component and a three-dimensional optical component; The two-dimensional optical component is used to acquire a two-dimensional image of the blade under test, so as to determine the length of the blade under test based on the two-dimensional image; the three-dimensional optical component is used to acquire a three-dimensional point cloud image of the blade under test, so as to determine the blade tip height, airfoil tolerance and blade pitch angle based on the three-dimensional point cloud image.

[0011] Optionally, the clamping mechanism includes: a preset fixing platform and at least one clamp disposed on the preset fixing platform, wherein the at least one clamp is used to fix and clamp at least one blade of different configuration.

[0012] Optionally, the clamping mechanism further includes a rotary motor, which is mounted on the preset fixed platform, and at least one clamp is fixedly mounted on the preset fixed platform for changing the attitude of the blade to be tested.

[0013] Optionally, the clamping mechanism further includes a counterweight assembly disposed on the preset fixed platform.

[0014] Secondly, another embodiment of this application provides a blade static detection method, applied to a computer device communicatively connected to the blade static detection device described in any of the first aspects above, the method comprising: The pressure data of the blade under test collected by the pressure detection mechanism and the optical data of the blade under test collected by the optical detection mechanism are obtained in the blade static testing equipment. Based on the pressure data, determine the physical property parameters of the blade under test; Based on the optical data, the external dimensions of the blade under test are determined.

[0015] The beneficial effects of this application are: This application provides a static testing device and method for propeller blades. The static testing device includes: a base, a clamping mechanism, a pressure detection mechanism, and an optical detection mechanism disposed on the base; wherein, the pressure detection mechanism and the clamping mechanism are disposed on a predetermined side of the base; the optical detection mechanism is slidably disposed on the bottom of the base to slide on a plane perpendicular to the bottom; the clamping mechanism is used to clamp and fix the blade under test, the pressure detection mechanism is used to collect pressure data of the blade under test to detect the physical property parameters of the blade under test, and the optical detection mechanism is used to collect optical data of the blade under test to detect the dimensional data of the blade under test. The static testing device for propeller blades in this application integrates the pressure detection mechanism and the optical detection mechanism on the same device, which can simultaneously detect the physical property parameters and optical data of the blade under test, avoiding the problems of increased measurement time and inaccurate measurement caused by repeatedly clamping measuring tools. Attached Figure Description

[0016] To more clearly illustrate the technical solutions of the embodiments of this application, the accompanying drawings used in the embodiments will be briefly introduced below. It should be understood that the following drawings only show some embodiments of this application and should not be regarded as a limitation of the scope. For those skilled in the art, other related drawings can be obtained based on these drawings without creative effort.

[0017] Figure 1 A schematic diagram of the structure of a propeller blade static testing device provided in an embodiment of this application; Figure 2 A schematic diagram of a pressure detection mechanism in a propeller blade static testing device provided in an embodiment of this application; Figure 3 A force analysis diagram of a first pressure sensor provided in an embodiment of this application; Figure 4This is a schematic diagram of the optical detection structure in a propeller blade static detection device provided in an embodiment of this application; Figure 5 This is a schematic diagram of the clamping mechanism in a propeller blade static testing device provided in an embodiment of this application; Figure 6 A schematic diagram of the drive circuit in a propeller blade static detection device provided in this application embodiment; Figure 7 This is a flowchart illustrating a method for static testing of a propeller blade, as provided in an embodiment of this application. Detailed Implementation

[0018] To make the objectives, technical solutions, and advantages of the embodiments of this application clearer, the technical solutions of the embodiments of this application will be clearly and completely described below with reference to the accompanying drawings. It should be understood that the accompanying drawings in this application are for illustrative and descriptive purposes only and are not intended to limit the scope of protection of this application. Furthermore, it should be understood that the schematic drawings are not drawn to scale. The flowcharts used in this application illustrate operations implemented according to some embodiments of this application. It should be understood that the operations in the flowcharts may not be implemented in sequence, and steps without logical contextual relationships may be reversed or implemented simultaneously. In addition, those skilled in the art, guided by the content of this application, may add one or more other operations to the flowcharts, or remove one or more operations from the flowcharts.

[0019] Furthermore, the described embodiments are merely some, not all, of the embodiments of this application. The components of the embodiments of this application described and illustrated herein can typically be arranged and designed in various different configurations. Therefore, the following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely to illustrate selected embodiments of the application. All other embodiments obtained by those skilled in the art based on the embodiments of this application without inventive effort are within the scope of protection of this application.

[0020] It should be noted that the term "comprising" will be used in the embodiments of this application to indicate the presence of the features declared thereafter, but does not exclude the addition of other features.

[0021] To clearly describe the propeller blade static testing device provided in the embodiments of this application, the device provided in the embodiments of this application will be described below with reference to several accompanying drawings. Figure 1 This is a schematic diagram of the structure of a propeller blade static testing device provided in an embodiment of this application, as shown below. Figure 1As shown, the blade static testing equipment includes: a base 100, a clamping mechanism 200 disposed on the base, a pressure testing mechanism 300, and an optical testing mechanism 400.

[0022] The pressure detection mechanism 300 and the clamping mechanism 200 are disposed on a predetermined side of the base 100; the optical detection mechanism 400 is slidably disposed on the bottom of the base to slide on a plane perpendicular to the bottom; the base 100 is made of a rigid material such as marble, which can ensure the overall rigidity and stability of the base 100. The pressure detection mechanism 300 and the clamping mechanism 200 may be disposed on either the left or right side of the base 100, and this embodiment of the application does not limit this.

[0023] The clamping mechanism 200 is used to clamp and fix the blade 500 under test. The pressure detection mechanism 300 is used to collect pressure data of the blade 500 under test to detect its physical property parameters. The optical detection mechanism 400 is used to collect optical data of the blade 500 under test to detect its dimensional data. The clamping mechanism 200 is positioned above the pressure detection mechanism 300 to clamp and fix the blade 500 under test, allowing the pressure detection mechanism 300 to collect its pressure data. The clamping mechanism 200 can fix the blade 500 under test by setting a clamping part to fix the blade 500 under test in the clamping mechanism 200, and then connect the blade 500 under test to the fixing part of the clamping mechanism 200 with screws.

[0024] This application provides a static testing device for propeller blades. The device includes a base, a clamping mechanism mounted on the base, a pressure detection mechanism, and an optical detection mechanism. The pressure detection mechanism and the clamping mechanism are located on a predetermined side of the base. The optical detection mechanism is slidably mounted on the bottom of the base, allowing it to slide on a plane perpendicular to the bottom. The clamping mechanism is used to clamp and fix the propeller blade under test. The pressure detection mechanism is used to collect pressure data from the propeller blade under test to detect its physical property parameters. The optical detection mechanism is used to collect optical data from the propeller blade under test to detect its dimensional data. This static testing device integrates the pressure detection mechanism and the optical detection mechanism into a single device, allowing simultaneous detection of both the physical property parameters and optical data of the propeller blade under test. This avoids the problems of time-consuming and inaccurate measurements caused by repeatedly clamping measuring tools.

[0025] Based on the above embodiments, the physical property parameters include weight. Therefore, this application provides a schematic diagram of a pressure detection mechanism in a propeller blade static testing device. Figure 2 This is a schematic diagram of a pressure detection mechanism in a propeller blade static testing device provided in an embodiment of this application, as shown below. Figure 2As shown, the pressure detection mechanism 300 includes: a first pressure sensor 301, which is disposed on a preset side. The first pressure sensor 301 is used to collect gravity data of the blade 500 under test, so as to calculate the weight of the blade 500 under test based on the gravity data.

[0026] The first pressure sensor 301 is a three-point supported pressure sensor. Specifically, the first pressure sensor 301 includes three pressure sensors, which are spaced equally to form an equilateral right triangle.

[0027] Optionally, the sensor data of the three pressure sensors in the first pressure sensor 301 when the blade to be tested 500 is not placed is obtained as the first weight data, and the sensor data of the three pressure sensors in the first pressure sensor 301 when the blade to be tested 500 is placed is obtained as the second weight data. The weight of the blade to be tested 500 is obtained by subtracting the second weight data from the first weight data.

[0028] In this embodiment, the first pressure sensor is a three-point supported pressure sensor, which is mounted on a preset side. The first pressure sensor is used to collect gravity data of the blade under test, and to calculate the weight of the blade based on the gravity data. This application simplifies the entire measurement process by collecting gravity data to calculate the weight of the blade, ensuring that the three support points provide better support and reducing measurement errors caused by uneven installation.

[0029] Based on the above embodiments, the physical property parameters also include: center of mass position and static moment; continuing to combine Figure 2 As shown, the pressure detection mechanism 300 also includes a second pressure sensor 302, which is disposed on a preset side. The second pressure sensor 302 is used to collect auxiliary pressure data of the blade 500 under test, so as to calculate the center of mass position and static torque of the blade 500 under test based on the auxiliary pressure data and weight.

[0030] The second pressure sensor 302 is a knife-edge balanced pressure sensor, which includes a knife edge and a pressure sensor.

[0031] The second pressure sensor 302 is disposed between the first pressure sensor 301 and the clamping mechanism 200.

[0032] Optionally, the second pressure sensor 302 acquires the first auxiliary pressure data when the blade to be tested 500 is not placed. The second auxiliary pressure data F after the blade is placed, and the position of the sensor in the second pressure sensor 302 from the blade edge. .

[0033] Optionally, based on the first auxiliary pressure data Second auxiliary pressure data F, sensor position distance from the cutting edge and weight The X-axis centroid coordinate of the blade 500 to be tested is obtained by calculating using the preset formula (1).

[0034] (1) Optionally, the product of the X-axis centroid coordinate of the blade under test 500 and the weight of the blade under test can be used as the static torque.

[0035] In this embodiment, the second pressure sensor is a knife-edge balanced pressure sensor. This sensor is used to collect auxiliary pressure data of the blade under test, and to calculate the center of mass position and static torque of the blade based on the auxiliary pressure data and its weight. This application utilizes the second pressure sensor to quickly capture pressure changes in the blade under test under different conditions, thereby more accurately calculating the center of mass position and static torque.

[0036] Based on the above embodiments, the physical property parameters also include: the position of the center of mass and the static moment. Figure 2 The pressure detection mechanism also includes a first lever arm sensor, a second lever arm sensor, and a third lever arm sensor, all of which are fixedly mounted on a preset side (not shown in the figure).

[0037] The first, second, and third lever arm sensors are used to collect the first, second, and third lever arm data of the blade under test, respectively, to calculate the centroid position and static moment of the blade under test based on the first, second, and third lever arm data. Specifically, the first, second, and third lever arm sensors are used to collect the lever arms of the three pressure sensors in the first pressure sensor 301. Based on the pressure and lever arms of the three pressure sensors in the first pressure sensor 301, the X-axis centroid coordinate and static moment of the blade under test 500 are calculated. The calculation process for the Y-axis centroid coordinate is the same as that for the X-axis centroid coordinate, and will not be elaborated further in this embodiment.

[0038] For example, Figure 3 A force analysis diagram of a first pressure sensor provided in an embodiment of this application is shown below. Figure 3 As shown, the pressure of the three pressure sensors is measured when no test is performed. , as well as The lever arms of the three pressure sensors , as well as , The force of the clamping mechanism when the blade to be tested is not placed. The coordinates of the centroid of the clamping mechanism when the blade to be tested is not placed.

[0039] After placing the blade to be tested, the pressure of the three pressure sensors at the time of placement. , as well as The lever arms of the three pressure sensors , as well as , The force of the clamping mechanism when placing the blade to be tested. The coordinates of the centroid of the clamping mechanism when placing the blade to be tested are given. The centroid coordinates of the X-axis can be determined according to the principle of force balance and the preset formulas (2)-(4).

[0040] (2) (3) (4) Optionally, the product of the X-axis centroid coordinate of the blade under test 500 and the weight of the blade under test can be used as the static torque.

[0041] Optionally, the X-axis centroid coordinates and static moment can be determined by a second pressure sensor, and the Y-axis centroid coordinates can be determined by a first torque sensor, a second torque sensor, and a third torque sensor, thereby determining the centroid of the blade under test.

[0042] In this embodiment, the first torque sensor, the second torque sensor, and the third torque sensor are used to collect first torque data, second torque data, and third torque data of the blade under test, respectively, so as to calculate the position of the center of mass and the static torque of the blade under test based on the first torque data, second torque data, and third torque data. This application can more comprehensively reflect the weight distribution of an object and more accurately determine the position of the center of mass.

[0043] Based on the above embodiments, the external dimensional data includes: length, tip height, airfoil tolerance, and pitch angle. Therefore, this application provides a schematic diagram of the optical detection structure in a propeller blade static inspection device. Figure 4 This is a schematic diagram of the optical detection structure in a propeller blade static inspection device provided in an embodiment of this application, as shown below. Figure 4 As shown, the optical inspection mechanism 400 includes: a two-dimensional optical component 401 and a three-dimensional optical component 402; The two-dimensional optical component 401 is used to acquire a two-dimensional image of the blade under test, so as to determine the length of the blade under test based on the two-dimensional image; the three-dimensional optical component 402 is used to acquire a three-dimensional point cloud image of the blade under test, so as to determine the blade tip height, airfoil tolerance and blade pitch angle based on the three-dimensional point cloud image.

[0044] The two-dimensional optical component 401 is disposed between the three-dimensional optical components 402, which are respectively disposed above and below the optical detection mechanism 400. The length of the blade under test is the straight-line distance from the root to the tip of the blade; the tip height of the blade under test is the height of the blade tip relative to the horizontal plane; the airfoil tolerance of the blade under test is the deviation between the actual size and the design size of the blade airfoil; and the pitch angle of the blade under test is the angle between the blade chord and the plane of rotation.

[0045] Optionally, the two-dimensional optical component 401 acquires a two-dimensional image of the blade under test. Let the centers of the two bushing holes on the blade be points A and B, respectively. Let point A be the origin O of the blade coordinate system. Let the direction from O to B be the positive Y-axis, and let the direction perpendicular to the Y-axis and pointing towards the blade tip be the positive X-axis. The blade tip plane profile obtained in the two-dimensional image is curve C. The two bushing holes on the blade are used to connect the blade to the hub and are respectively located at the root of the blade.

[0046] Taking point O as the origin, the direction from O to B as the positive Y-axis, and the direction perpendicular to the Y-axis and pointing towards the blade tip as the positive X-axis, the blade tip plane profile obtained from the 2D image is curve C. Using the Y-axis as a reference, find a straight line L that is parallel to the Y-axis and tangent to curve C. Let P be the point of tangency between line L and curve C, and take the coordinate value xP of point P on the X-axis. Define xP as the length of the blade.

[0047] Optionally, a 3D optical component is used to scan the blade bushing surface to obtain 3D data of the bushing surface, determine the plane S, and use the 3D optical component to scan the position of the blade at the 0.98R section. On the 0.98R section, the highest point of this section is found. A perpendicular line is drawn from the highest point to the bushing surface S, and the intersection of the perpendicular line and the bushing surface S is P. The distance h from the highest point to point P is calculated. This distance is the height of the blade tip relative to the bushing surface. Adding h to the constant c yields the blade tip height.

[0048] Optionally, a three-dimensional point cloud image of the blade under test is acquired by a three-dimensional optical component, and a preset point cloud image of the blade under test is obtained. The preset point cloud image is a point cloud image constructed during the design process of the blade under test. From the three-dimensional point cloud image and the preset point cloud image, the three points with the closest coordinates are determined, and the actual fitting curve and the preset fitting curve are fitted respectively. The actual fitting curve and the preset fitting curve are compared to determine the airfoil tolerance.

[0049] Optionally, the pitch angle is calculated by using inverse trigonometric functions based on the actual coordinates of the leading edge endpoint and the trailing edge endpoint of the blade in the three-dimensional point cloud image of the blade to be tested acquired by the three-dimensional optical component. If the airfoil tolerance is less than the preset threshold, the pitch angle is qualified; otherwise, the pitch angle is unqualified.

[0050] Specifically, since the blade under test is measured on a horizontal plane, the horizontal coordinates of the actual coordinates of the leading edge endpoint and the trailing edge endpoint of the blade under test are the same. Therefore, based on the vertical axis (y-axis) and the normal axis (z-axis) of the actual coordinates of the leading edge endpoint and the trailing edge endpoint of the blade under test, the horizontal coordinates of the blade under test are obtained by... ), actual coordinates of the trailing edge endpoint ( The pitch angle of the blade to be tested is calculated using the preset formula (5) and the preset formula (5).

[0051] (5) In this embodiment, the optical inspection mechanism includes a two-dimensional optical component and a three-dimensional optical component. The two-dimensional optical component is used to acquire a two-dimensional image of the blade under test to determine the length of the blade based on the two-dimensional image; the three-dimensional optical component is used to acquire a three-dimensional point cloud image of the blade under test to determine the blade tip height, airfoil tolerance, and pitch angle based on the three-dimensional point cloud image. This application utilizes the two-dimensional optical component to acquire high-resolution two-dimensional images, clearly displaying the details of the blade under test, and the three-dimensional optical component to acquire a three-dimensional point cloud image of the blade under test, improving the accuracy of the measurement of the blade under test, while providing planar and three-dimensional inspection data for a more comprehensive evaluation of the quality of the blade under test.

[0052] Based on the above embodiments, this application also provides a structural schematic diagram of the clamping mechanism in a propeller blade static testing device. Figure 5 This is a schematic diagram of the clamping mechanism in a propeller blade static testing device provided in an embodiment of this application, as shown below. Figure 5 As shown, the clamping mechanism 200 includes: a preset fixing platform 201 and at least one clamp 202 disposed on the preset fixing platform, wherein the at least one clamp 202 is used to fix and clamp at least one blade of different configuration.

[0053] The clamp 202 can be a double-sided opening and closing clamp, a flexible clamping mechanism, or a soft material clamp. This application embodiment does not limit this.

[0054] Optionally, the clamping mechanism 200 further includes a rotary motor 203, which is mounted on a preset fixed platform 201, and at least one clamp 202 is fixedly mounted on the preset fixed platform 201 for changing the attitude of the blade to be tested.

[0055] Optionally, the clamping mechanism 200 may further include a counterweight component 204 disposed on a preset fixed platform 201.

[0056] The counterweight component 204 is used to ensure that the center of mass of the clamping mechanism 200 is within the range of the first pressure sensor when the blade 500 to be tested is clamped and when the blade 500 to be tested is not clamped.

[0057] In this application embodiment, the clamping structure includes a clamp, a rotary motor, and a counterweight assembly. The clamp in this application can provide stable fixation to ensure the positional accuracy of the blade during the detection or processing process. The rotary motor can quickly adjust the attitude of the blade as needed, and the counterweight assembly can maintain the accuracy of the blade measurement.

[0058] Optionally, based on the above embodiments, the blade static testing equipment further includes: a drive circuit and a control circuit. Figure 6 This is a schematic diagram of the drive circuit in a propeller blade static testing device provided in an embodiment of this application, as shown below. Figure 6 As shown, the drive circuit is connected to the power supply via N (neutral), L (live), and E (ground). The X-axis driver XA probe and Y-axis driver XA probe in the drive circuit are connected to the optical inspection mechanism, allowing the optical inspection mechanism to move along the X and Y axes at the bottom of the base. The W-axis driver power connector is connected to the upper part of the optical inspection mechanism, allowing the three-dimensional optical components to move in the W-axis direction. The J-axis driver power connector is connected to the clamping mechanism, allowing the rotary motor in the clamping mechanism to move along the J-axis. The OUT signal in the limit switch is used to control the movement distance of the optical inspection mechanism in the positive and negative directions of the X, Y, and Z axes, and the rotation degree of the clamping mechanism in the W and U axes. The control circuit in this application is connected to the power supply in the blade static inspection equipment and to the sensors in the blade static inspection equipment. The movement degree of each device is determined by detecting the signals from the sensors, and an emergency stop switch is set to control the movement degree of each device in the blade static inspection equipment.

[0059] Based on the same inventive concept, this application also provides a method for static blade detection, using a computer device communicatively connected to the aforementioned static blade detection equipment. Figure 7 This is a flowchart illustrating a method for static detection of a propeller blade provided in an embodiment of this application, as shown below. Figure 7 As shown, the method includes: Step 701: Obtain the pressure data of the blade under test collected by the pressure detection mechanism in the blade static testing equipment and the optical data of the blade under test collected by the optical detection mechanism.

[0060] The pressure data includes: gravity data of the blade under test and auxiliary pressure data of the blade under test. The optical data includes: two-dimensional images and three-dimensional point cloud images of the blade under test.

[0061] Optionally, the gravity data of the blade under test is collected by the first pressure sensor in the pressure detection mechanism, and the auxiliary pressure data of the blade under test is collected by the second pressure sensor in the pressure detection mechanism.

[0062] Optionally, a two-dimensional image of the blade under test is acquired using a two-dimensional optical component in the optical inspection mechanism, and a three-dimensional point cloud image of the blade under test is acquired using a three-dimensional optical component in the optical inspection mechanism.

[0063] Step 702: Determine the physical property parameters of the blade to be tested based on the pressure data.

[0064] The physical properties include: weight, center of mass position, and static moment.

[0065] Optionally, the weight of the two blades to be tested can be calculated based on the gravity data of the blades to be tested collected by the first pressure sensor. The specific calculation process has been described in detail above and will not be repeated here.

[0066] Optionally, the position of the center of mass and the static moment of the blade under test are calculated based on the auxiliary pressure data and weight of the blade collected by the second pressure sensor. The specific calculation process has been described in detail above and will not be repeated here.

[0067] Step 703: Determine the external dimensions of the blade to be tested based on the optical data.

[0068] The external dimensions include: length, blade tip height, airfoil tolerance, and blade pitch angle.

[0069] Optionally, the length of the blade to be measured can be determined based on the two-dimensional image acquired by the two-dimensional optical component. The specific calculation process has been described in detail above and will not be repeated here.

[0070] Optionally, the tip height, airfoil tolerance, and pitch angle of the blade under test can be determined based on the three-dimensional point cloud image acquired by three-dimensional optical minimum acquisition. The specific calculation process has been described in detail above and will not be repeated here.

[0071] This application provides a method for static testing of propeller blades. The method acquires pressure data of the propeller blade under test collected by a pressure testing mechanism and optical data of the propeller blade under test collected by an optical testing mechanism within a static testing device. Based on the pressure data, the physical property parameters of the propeller blade under test are determined; based on the optical data, the external dimensions of the propeller blade under test are determined. This application, by setting up a static testing device, can simultaneously measure both the physical property parameters and the external dimensions of the propeller blade, avoiding the problems of excessively long measurement times and inaccurate measurements caused by setting up and clamping multiple measuring tools.

[0072] Those skilled in the art will clearly understand that, for the sake of convenience and brevity, the specific working processes of the systems and devices described above can be referred to the corresponding processes in the method embodiments, and will not be repeated here. In the several embodiments provided in this application, it should be understood that the disclosed systems, devices, and methods can be implemented in other ways. The device embodiments described above are merely illustrative. For example, the division of modules is only a logical functional division, and in actual implementation, there may be other division methods. Furthermore, multiple modules or components can be combined or integrated into another system, or some features can be ignored or not executed. Another point is that the displayed or discussed mutual coupling or direct coupling or communication connection can be through some communication interfaces; the indirect coupling or communication connection of devices or modules can be electrical, mechanical, or other forms.

[0073] Furthermore, the functional units in the various embodiments of this application can be integrated into one processing unit, or each unit can exist physically separately, or two or more units can be integrated into one unit. If the functions are implemented as software functional units and sold or used as independent products, they can be stored in a computer-readable storage medium. Based on this understanding, the technical solution of this invention, or the part that contributes to the prior art, or a part of the technical solution, can be embodied in the form of a software product. This computer software product is stored in a storage medium and includes several instructions to cause a computer device (which may be a personal computer, server, or network device, etc.) to execute all or part of the steps of the methods described in the various embodiments of this invention. The aforementioned storage medium includes: USB flash drives, portable hard drives, read-only memory (ROM), random access memory (RAM), magnetic disks, optical disks, and other media capable of storing program code.

[0074] The above are merely specific embodiments of this application, but the scope of protection of this application is not limited thereto. Any changes or substitutions that can be easily conceived by those skilled in the art within the scope of the technology disclosed in this application should be included within the scope of protection of this application.

Claims

1. A propeller blade static testing device, characterized in that, The blade static testing equipment includes: a base, a clamping mechanism disposed on the base, a pressure testing mechanism, and an optical testing mechanism; The pressure detection mechanism and the clamping mechanism are disposed on a predetermined side of the base, with the clamping mechanism disposed above the pressure detection mechanism; the optical detection mechanism is slidably disposed on the bottom of the base so as to slide on a plane perpendicular to the bottom. The clamping mechanism is used to clamp and fix the blade under test; the pressure detection mechanism is used to collect the pressure data of the blade under test to detect the physical property parameters of the blade under test; and the optical detection mechanism is used to collect the optical data of the blade under test to detect the external dimensions of the blade under test. The physical property parameters include: weight; the pressure detection mechanism includes: a first pressure sensor, which is disposed on the preset side; The first pressure sensor is used to collect the gravity data of the blade under test, so as to calculate the weight of the blade under test based on the gravity data. ; The physical property parameters also include: the position of the center of mass and the static moment; The pressure detection mechanism further includes: a second pressure sensor, which is a knife-edge balanced pressure sensor. The second pressure sensor includes a knife edge and a pressure sensor, and is disposed between the first pressure sensor and the clamping mechanism. The second pressure sensor is located on the preset side and is used to collect auxiliary pressure data of the blade under test, so as to calculate the center of mass position and static torque of the blade under test based on the auxiliary pressure data and the weight; the second pressure sensor also acquires first auxiliary pressure data when the blade under test is not placed. Second auxiliary pressure data after placing the blade to be tested and the position of the sensor in the second pressure sensor from the blade edge. Based on the first auxiliary pressure data, the second auxiliary pressure data, the position of the sensor relative to the blade, and the weight, a preset formula is used... The X-axis centroid coordinates of the blade under test were calculated. The external dimensional data includes: length, blade tip height, airfoil tolerance, and blade pitch angle; The optical inspection mechanism includes: a two-dimensional optical component and a three-dimensional optical component; The two-dimensional optical component is used to acquire a two-dimensional image of the blade under test, and to determine the length of the blade based on the two-dimensional image. The blade tip plane profile obtained in the two-dimensional image is curve C. Taking the Y-axis as the reference, a straight line parallel to the Y-axis and tangent to curve C is found. Let P be the point of tangency between the straight line and curve C. Take the coordinate value of point P on the X-axis and define the coordinate value as the length of the blade. Let the centers of the two bushing holes of the blade under test be points A and B, respectively. Let point A be the origin O of the blade coordinate system. Let the direction from O to B be the positive direction of the Y-axis. Let the direction perpendicular to the Y-axis and pointing to the blade tip be the positive direction of the X-axis. The three-dimensional optical component is used to acquire a three-dimensional point cloud image of the blade under test, so as to determine the blade tip height, airfoil tolerance, and blade pitch angle based on the three-dimensional point cloud image.

2. The device according to claim 1, characterized in that, The first pressure sensor is a three-point support pressure sensor; The physical property parameters also include: the position of the center of mass and the static moment; The pressure detection mechanism further includes: a first lever arm sensor, a second lever arm sensor, and a third lever arm sensor, wherein the first lever arm sensor, the second lever arm sensor, and the third lever arm sensor are all fixedly disposed on the preset side. The first lever arm sensor, the second lever arm sensor, and the third lever arm sensor are respectively used to collect the first lever arm data, the second lever arm data, and the third lever arm data of the three pressure sensors in the first pressure sensor, so as to calculate the center of mass position and static torque of the blade under test based on the first lever arm data, the second lever arm data, the third lever arm data, and the pressure of the three pressure sensors in the first pressure sensor.

3. The device according to claim 1, characterized in that, The clamping mechanism includes: a preset fixing platform and at least one clamp disposed on the preset fixing platform, wherein the at least one clamp is used to fix and clamp at least one blade of different configuration.

4. The device according to claim 3, characterized in that, The clamping mechanism further includes a rotary motor, which is mounted on the preset fixed platform, and at least one clamp is fixedly mounted on the preset fixed platform for changing the attitude of the blade to be tested.

5. The device according to claim 3, characterized in that, The clamping mechanism further includes a counterweight assembly disposed on the preset fixed platform.

6. A method for static detection of propeller blades, characterized in that, The method, applied to a computer device communicatively connected to the blade static testing device according to any one of claims 1-5, comprises: The pressure data of the blade under test collected by the pressure detection mechanism and the optical data of the blade under test collected by the optical detection mechanism are obtained in the blade static testing equipment. Based on the pressure data, determine the physical property parameters of the blade under test; Based on the optical data, the external dimensions of the blade under test are determined.

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